Report discussing tests to determine the aerodynamic characteristics of a model of a 45 degree swept-wing fighter airplane and to determine the loads on attached stores and detached missiles. An investigation into aileron-spoiler effectiveness, aileron hinge moments, and the effects of wing modifications of aerodynamic characteristics was also carried out at various Mach numbers. Results are presented, but caution is provided in regards to extrapolating results from the model onto a full-scale aircraft.

Report of an investigation using three rocket-propelled delta-wing-body combinations for a range of Mach numbers to determine the damping-in-pitch characteristics. All models were statically stable but dynamically unstable at transonic speeds. Information about trim, lift, and drag is also provided.

Memorandum presenting static longitudinal stability and control characteristics of a flare-stabilized body of revolution employing a movable portion of the flare surface as a pitch control determined for a range of Mach numbers, angles of attack, and control deflections. The variation of lift coefficient with pitching-moment coefficient for the basic configuration with control undeflected was found to be essentially linear, and the stability to increase slightly with increasing Mach number.

Report presenting a lateral-control investigation of 3- and 6-percent chord spoilers projecting on the upper surface of a wing of high-aspect ratio. The spoilers were found to give large rolling moments at Mach numbers below the Mach number corresponding to the break in the rolling-moment-coefficient curves. Results regarding section pressure distributions, rolling-moment characteristics, normal-force characteristics, pitching-moment characteristics, wing-torsional considerations, and hinge-moment characteristics are provided.

Report presenting an investigation using a single combustor from a 4600-pound-thrust turbojet engine to determine the amount of carbon deposition of AN-F-58 fuels and the effect of carbon formations in the combustor on the altitude operational limits. Three fuel blends conforming to AN-F-58 specification were prepared in order to determine the influence of boiling temperature and of aromatic content on carbon deposition. Results regarding carbon deposition and effect of carbon formations on altitude operational limits are provided.

Contains a few measurements of the variation of elevator angle and elevator force with Mach number at 30,000 feet altitude up to a Mach number of 0.85. These data show that the airplane possessed positive static longitudinal stability up to a Mach number of 0.80. A trim change in the nose-down direction occurred for Mach numbers above 0.82.

Report presenting a wind-tunnel investigation to determine the respective variations with Mach number of the static longitudinal stability, the drag, and the effectiveness of a constant-chord control surface for a tailless fighter aircraft with a triangular wing of aspect ratio 2.31.

Report presenting the results of an investigation to determine the effect of chord discontinuities and chordwise fences on the static longitudinal stability and wake characteristics of an airplane model with a 35-degree sweptback wing. The use of a fence or chord extension was found to cause a slight improvement in the static longitudinal stability of the basic wing alone. The force data and flow characteristics in the form of wake surveys and surface tufts are provided.

From Summary: "An investigation was made in the Langley high-speed 7- by 10-foot tunnel through a Mach number range from 0.60 to 0.93 to determine the effects on the chordwise pressure distributions of projecting various spoiler-type ailerons on a swept wing. The semispan 35 degree sweptback wing had an NACA 65A006 airfoil section, an aspect ratio of 4, and a taper ratio of 0.6. The results of the investigation are presented as curves of chordwise pressure distributions near the midspan of the spoilers (0.46-wing-semispan station)."

Report presenting an investigation of the stress-rupture and creep properties of hot-pressed molybdenum disilicide, which explored the stress-rupture properties, use of molybdenum disilicide at various temperatures, long-time strength, and a satisfactory method for creep and stress-rupture testing.

Memorandum presenting a simplified analysis to determine the effective thermal conductivity of a powder from the fraction of space occupied by the gas and conductivities of the solid and the gas which make up the powder. Tests were conducted to determine the conductivity of magnesium oxide powder in various gases at a range of temperatures. The effects of some of the factors neglected in the simplified analysis, such as bending of the heat-flow lines and the irregularity of the arrangement of the particles, were investigated and discussed.

Report presenting an investigation in the supersonic tunnel using a canard missile configuration designated as NACA RM-4. Measurements of lift, drag, and pitching moment were made over a range of Mach numbers and angles of attack. The data is presented without analysis.

Report presenting measurements of longitudinal stability and drag characteristics of a fin-stabilized body of revolution with a fineness ratio 12 at low angles of attack using the free-fall method. Information about the data obtained from testing as well as the experimental coefficients related to body normal-force, total longitudinal-force, and body moment with Mach number is provided.

Report presenting free-falling recoverable-model tests at transonic speeds on a model with a triangular wing of aspect ratio 3 and a 45 degree swept tail located in the chord plane of the wing. Static and dynamic longitudinal-stability data for the complete model, force and moment data for the major components of the model, and load distributions over the fuselage of the model were evaluated at a range of angles of attack. results regarding lift, drag, static longitudinal stability, dynamic longitudinal stability, horizontal-tail effectiveness, loading distributions over fuselage, and buffet boundary are provided.

Report presenting an investigation to determine the effects of two types of propeller-spinner junctures on the pressure-recovery characteristics of an NACA 1-series D-type cowl with an NACA 1-series spinner, in combination with a four-blade single-rotation propeller.

Report presenting an investigation at Mach numbers from 0.50 to 0.94 of the effects of two sizes of missiles in several combinations of spanwise and vertical positions on the aerodynamic characteristics of wing-fuselage combinations with a 46.7 degree sweptback wing and an essentially unswept wing. Results regarding the drag characteristics and lift and pitch characteristics are provided.

Report presenting an investigation in the supersonic pressure tunnel at two Mach numbers to determine the aerodynamic characteristics of several jet-spoiler controls on a wing having a 45 degree sweepback of the quarter-chord line, an aspect ratio of 3.5, a taper ratio of 0.3, and an NACA 65A005 airfoil section. Testing indicated that the jet-spoiler effectiveness increased with increasing angle of attack and correlated well with the momentum of jet flow.

Memorandum presenting an investigation in the Unitary Plan wind tunnel to determine the aerodynamic characteristics of a model of a 45 degree swept-wing fighter airplane, and to determine the loads on attached stores and detached missiles in the presence of the model. Results also included a determination of aileron-spoiler effectiveness, aileron hinge moments, and the effects of wing modifications on model aerodynamic characteristics. The results are presented with minimum analysis.

Report presenting a study of the effects of mass ratio on the transonic flutter characteristics of untapered 45 degree sweptback wings of aspect ratios 2 and 3.5. A given wing at a given Mach number fluttered at essentially a fixed dynamic pressure regardless of the individual values of the fluid velocity and density. Results regarding the experimental data, analytical results, and a comparison of the two, are provided.

"A theoretical method is presented for predicting the dynamic lateral stability characteristics of an airplane towed in tandem by a much larger airplane. Values of period and time to damp to one-half amplitude and rolling motions calculated by an analog computer have been correlated with results of two experimental investigations conducted in the Langley free-flight tunnel which were part of a U.S. Air Force program (Project FICON) to develop a satisfactory arrangement by which a bomber could tow a parasite fighter. In general, the theoretical results agree with the experimental results" (p. 1).

Report presenting estimates of the variation with Mach number of the aerodynamic characteristics of swept wings on the basis of airfoil section data combined with span-loading theory. Results regarding adjusted wing theory procedure and adjusted wing data procedure are provided.

A spin-recovery investigation has been conducted in the Langley 20-foot free-spinning tunnel on a 20-scale model modified to represent the McDonnell XF2H-1 airplane. The project included tests both with tip tanks installed and with the tanks removed. The results indicated that the recovery characteristics of the airplane would be satisfactory for all loadings by normal recovery technique (full reversal of the rudder, followed 1/2 turn later by movement of the elevator down). The rudder pedal and the elevator stick forces likely to be encountered in a spin should be within the capabilities of the pilot.

"The Lewis Flight Propulsion Laboratory of the National Advisory Committee for Aeronautics proposes to build a zero power research reactor facility which will be located in the laboratory grounds near Cleveland, Ohio. The purpose of this report is to inform the Advisory Committee on Reactor Safeguards of the U. S. Atomic Energy Commission in regard to the design of the reactor facility, the characteristics of the site, and the hazards of operation at this location. The purpose of this reactor is to perform critical experiments, to measure reactivity effects, to serve as a neutron source, and to serve as a training tool" (p. 1).